基于EA方法的飞行控制律设计与仿真

Design and Simulation of Flight Control Laws Based on EA Method

在飞行控制系统优化设计中,由于系统存在多输入、多输出的模型结构,古典控制方法无法应用到MIMO系统中,尤其现代控制方法设计过程中一次性计算出反馈控制器,导致应用过程中可靠性降低,对古典飞行控制系统控制结构进行优化设计。控制系统内回路采用EA方法,外回路适当引入误差积分控制和前馈比例控制,进而针对广义被控对象直接进行控制律设计与仿真。运用根轨迹方法对控制系统进行验证分析,并根据实际需求对控制律进行适当改进。仿真结果表明,特征结构配置方法能够较好的与古典控制理论相结合,完成指令跟踪控制律设计,且具有很好的鲁棒性和动态特性,新的控制结构应用起来方便有效。

Study the Eigenstructure assignment （EA） method. The control structure of the classical control system was optimized, according to the problems that the classical control method can not be used in MIMO system as well as the low reliability resulted from the fast and direct design process of EA method. The inner loop of control sys- tem was designed by EA method, and error integrator control and feed forward P control were adopted in outer loop properly. Then the control laws were designed to the generalized controlled object, the simulation flight control system was realized. Then root - locus method was used to analyze the stability of control system. And proper improvements were made according to actual requirements. Simulation results show that the EA method can be combined with classical control theory perfectly, and complete control law design of the tracking tasks, which has good robustness and dynamic characteristics. The new control structure is convenient and effective.